University Student Launch InitiativeUniversity Student Launch Initiative

System Requirements ReviewSystem Requirements ReviewPayload Team

September 3, 2009

OverviewOverview

• Purpose of System Requirements Review (SRR)• Mission Statement• Market Analysis and Benchmarking• Physical Requirements• Functional Description• Major Components • Design Drawing• Manufacturing Methods• Resources and Facilities• Safety Considerations• Cost Analysis• Activity Plan• Summary

Purpose of SRRPurpose of SRR

• To review, update, and establish the mission and system requirements

• To confirm performance requirements• To establish that the cost and design are

feasible• To evaluate system safety and manufacturing

methods

Mission StatementMission Statement

• Charger Rocket Works is a group of senior engineering students that seek to build a high power rocket designed to fly to exactly one mile for the USLI Competition.

• The payload team seeks to design a payload that will measure the condition a deployable UAV will under go in flight and deployment of a parafoil.

Market Analysis and Market Analysis and BenchmarkingBenchmarking

• Past UAH Projects (from www.sli.uah.edu)

-All UAH Rockets have had a payload to take telemetry data and video from the flights

-2004 Carried a payload that tested the stress strain in a carbon fiber body

-2008-2009 Nosecone carried a retracting pitot tube plus the instrument to track the telemetry in the nosecone.

Market Analysis and Market Analysis and BenchmarkingBenchmarking

-2008-2009 also carried a payload above the motor to test measure the thrust generated by the rocket.

• Last year winner Florida Institute of Technology carried a payload that measured effects of gravity on the sloshing in side a tank.

• Georgia Tech last year carried a payload that measured the separation of air around their rocket.

Physical RequirementsPhysical Requirements

The diameter, length, and length are TBD with recover and structure teams help:

1. The diameter and length will be based for the most part on the parafoil deployment.

2. A general weight specification will be determined once specific components are chosen.

Functional DescriptionFunctional Description

Data Gathering Function• Function:

• Telemetry – GPS– Five Hole Probe– Altimeter

• Measurement for UAV– Internal Pressure Cell– Internal Thermocouples– Load cells– Sensor to measure vibrations

• Video recording

• Objective:– Determines the conditions that

a Deployable UAV payload would have to go through

Controlled Landing Function

• Function:• Guidance

– GPS– IMU (Inertial Measurement Unit)

• Control– Parasail– Servos

• Communication– Transceiver– Antenna

• Objective:• Test Guidance & Navigation

System in Conjunction With a Parafoil

• Telemetry (GPS, Five Hole Probe, Altimeter)

• Measurement for UAV (Pressure sensor, Thermocouple, and load cells)

Autopilot Data Acq.

Major ComponentsMajor Components

Automated Lander Controlled Landing Function

COTS = Commercial Off-The-ShelfGS = Ground Station

GPS

IMU

Guidance

Actuator

D/T Device

C&D

Comm

GS**

Sensors

• Navigation (GPS & IMU)

• Guidance (AVR/PIC MCU(s), COTS* Autopilot)

• Actuator (Servo(s), Brushless motor(s))

• Descent/Thrust Device (Parafoil, Rotors)

• Sensor (Pressure, Accelerometer, Temperature, gyroscope, etc.)

• Communication (Transceiver, Antenna)

• Command & Data (MCU, COTS Data Logger)

Design DrawingDesign Drawing

May Have Sabot

Body Tube Experiment

Airfoil

Nose Cone

Deployable Airfoil With Experiment Pitot Tube

Design DrawingDesign DrawingDeployable Lander

Possible Airfoil Payload

Manufacturing Manufacturing MethodsMethods

• A few process are as follows:• Drilling• Soldering• Wiring• Machining and Assemble as needed

Resources and Resources and FacilitiesFacilities

• Resources• MathCAD• Matlab• SolidEdge• Microcontroller IDE (AVR Studio or PICC)• PCB CAD (ExpressPCB)

• Facilities• SLI Lab• ASGC/SHC Lab• MAE Machine Shop

Safety ConsiderationsSafety Considerations

• Possible failure modes:– Payload does not deploy at apogee

– Parachute on payload does not deploy

– Automated guidance system does not work

– Weight and size of payload could create structural instability (e.g. Vanderbilt UAV disaster)

• Initial solutions:– Create a payload deployment system similar to one used in the CanSat

competition

– Two altimeters onboard payload for redundancy purposes

– Have a manual switch for guidance system, if guidance fails, the payload will still return safely

– Payload will have a GPS system allowing fast location of payload

– This payload will be MUCH smaller than Vanderbilt’s and shouldn’t take up much more space than past payloads.

Safety ConsiderationsSafety Considerations

• NAR Requirements:– Payload must be recovered safely– Must be made of lightweight materials– Payload cannot cause rocket to weigh more than one-third of the

average thrust of the motor.– Parafoil and instrumentation must be flame resistant.

• USLI Handbook Requirements:– Separation at apogee is allowed, but it increases the risk of floating

outside recovery area.

– Payload must be scientific in nature.

– Payload must re-coverable and re-usable.

– Be aware of hazardous materials, and environmental concerns: no hazardous materials or environmental concerns are projected for this experiment.

Cost AnalysisCost Analysis

1. GPS: 75

2. IMU: 75

3. Parafoil: TBD

4. Pressure Sensor: 10

5. Accelerometer: 30

6. Temperature sensor: 8

7. GPS Comm: 100

8. Materials: TBD

9. Transceiver: 63

10. Servos: 60

11. Pressure Sensor: 10

12. Accelerometer: 30

13. Temperature sensor: 8

14. Transceiver: 63

15. Materials: TBD

16. Parachute: 10

17. Load cell: TBD

18. Five Hole Probe: TBD

Activity PlanActivity Plan

SRR Task Assignments:

•Patrick Giddens (Team Leader)•Mission Statement and Review Past Team Benchmarks•Micro G Concept

•Seiya Shimizu•Automated Lander Concept•Research Concepts

•Matthew Statham•Physical Requirements•Cost Analysis•Research Concepts

•Michael MacDonald•Safety Considerations•Summary•Research Concepts

•Danny Bottoms•Design Drawing•Research Concepts

SummarySummary

• Payload will have two functions:– In flight measurements

• Measurements will be made during thru the flight that will be useful in deterring what condition a UAV payload will ender before deployment.

– Automated return via controlled parafoil

• Measurements will be made during return and data will be useful for future UAV payload endeavors.

• The current payload concept fits the basic safety and feasibility requirements.

• Modifications and further specification of design are

required.